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9 4,000,609 10 be provided to circulate oil from outlet port 254 to inlet 32 during engine operation functions to cool bearing port 188 through bearing 176 out of port 190 into 176, turbine rotor 28, and slinger ring 26. This cooling passages222and224throughbearings220and243 actionisimportanttotheefficientoperationofengine and back into gear cavity 230. The oil level is gear 10 and enables the use of relatively inexpensive materi cavity230shouldbemaintainedinaccordancewith alsforthevariouscooledcomponents. acceptablegearreducerstandards. The vaporized fuel and air mixes in combustion A drain'plug 256 is located in‘housing 94 and ’ chamber36andisignitedbyglowplug268.Theburnt projects into combustion chamber 36'through forward section 38. Plug 256 islocated at the lowest part of combustion chamber 36 when engine 10 isinan opera tiveposition.A pluralityofspaceddrainholes258are provided between forward section‘38and surface 92 and communicate with a cup-like reservoir 260 in plug 256‘. A retaining plug 262 encloses the open end of reservoir 260 and has a fuel drain passage 261 commu nicating with combustion chamber 36 ‘and reservoir 260.‘ Reservoir260 communicates with the atmosphere through a drain passage 264. Passage 264 isopened and closed by astem valve 266 having a closing ring whichrestrictdrainpassage264andisnormallycon 20 throughpassages158innozzleplate156,throughthe cave and opens toward combustion chamber 36 and a cylindrical shaped stem located in an opening in plug 256.When engine10isoperating,theflowcausedby_ pressurecreatedbyincomingairforcestheclosingring slowlymovesalongthewallsofhousings94and138 intheareaofdrainpassage264?attosealdrainpas 25 andabsorbsheattotherebycoolthehousings.The sage 264. Upon a reduction of pressure, which occurs when engine 10isturnedoff,theclosingringreturnsto its concave con?guration to permit noncombusted liquid fuel in combustion chamber 36 and housing 94 to ?ow into reservoir 260 through passages 261 and holes 258 to be drained from engine 10. heated gas in the cavity reenters the incoming air ?ow to combustion chamber 36 to be mixed with fuel and burned. When the shaft assembly 14 reaches an rpm to sup portself-sustainedoperation,theinputdrivetooutput shaft242isremoved.Byvaryingthefuelinputthereaf ter,thespeedofengine10canbecontrolled.Anap propriatefuelcontrolsystem(notshown)isusedto monitor fuel ?ow. The air inlet 18 provided between Diametricallyopposedfromdrainplug256isaglow plug268connectedtohousing94andprojectinginto combustion chamber 36 through forward section 38. Glowplug268comprisesanigniter270incombustion 35 transmission 16 and power section 12 reduces heat chamber 36 which is connected to a terminal 272 which is insulated from the main portion of the glow plug. Terminal 272 is intended to be connected to an electrical circuit which will pass a current ?ow through igniter 270 to make the igniter hot enough to ignite a 40 inlet did not separate the two components. Various fuel air mixture in combustion chamber 36. To operate engine 10, a power source, such as an electric motor, is connected to output shaft 242 to other design characteristics which have been previ ouslydescribedand/orillustratedfurtheraidtheobjec tive of reducing the cost of engine components as well as the objective of improving engine ef?ciency. rotate shaft assembly 14. Rotation of compressor rotor 24forcesairthroughairfilter20intoairinlet18and45 Whatisclaimedis: then into compressor inlet passage 116. The incoming air is forced through compressor rotor 24 and then through passages 130 de?ned by diffuser portion 119 of diffuser plate 118. The compressed air encircles forwardandrearwardsections38and40ofcombus 50 tion chamber 36 and filsthe annular cavity 274 de ?ned by exhaust housing 138 and the adjacent portion of intake housing 94. The thimble burners 74 direct the incoming air between rearward section 40 and nozzle plate156.Theairisforcedthroughthevariouslouvers 55 and passages into combustion chamber 36 to create a swirling, turbulent air mass. At the same time air is being forced through com pressor rotor 24, fuel is being injected in a liquid form into fuel inlet 184. The rotation of shaft assembly 14 60 forcestheincomingfuelradiallyoutwardlyagainstthe conical wall of fuel supply passage 32 and drives the fuel into the portion of passage 32 located in slinger ring 26; the fuel is thereafter slung radially outwardly through slinger ports 34 into combustion chamber 36. 65 After engine 10 has been operated for a period of time, the fuel vaporizes during its passage through passage 32. The fuel passing through and vaporizing in passage 1.A gasturbineenginecomprising: A. a shaft assembly having a central axis and includ l. a turbine having radial blades, and 2.acompressorhavingradialbladesandbeing axiallyspacedfromsaidturbine; B. a housing enclosing at least a portion of said shaft assembly; C. an annular nozzle plate supported by said housing and encircling said shaft assembly intermediate said turbine and said compressor, said nozzle plate having I. an annular one piece radially extending nozzle portion having cantilever vanes at least partially defining a plurality of radially extending nozzle passages in fluid communication with said tur bine, and 2. an annular axially extending hub portion project ing axially away from said turbine toward said compressor in juxtaposition to said shaft assem bly; and D. an annular liner de?ning a combustion chamber located between said compressor and said nozzle mixture expands and exhausts through the passage de?ned by outer portins 46 and 84 of forward and rearward sections 38 and 40. The burnt gases pass around thimble burners 74 heating these thimbles. Air passing through these thimbles from the compressor rotor 24 to combustion chamber 36 is thereby heated prior to combustion. The passage of such incoming air from compressor rotor 24 through thimbles 74 also cools thimbles 74 and thereby‘cools the exhaust gases. The exhaust gases are further cooled‘ by the introduc tionofcompressorairthroughdilutionpassages76and 110 in sections 38 and 40. The exhaust gases then pass blades on turbine rotor 28 to drive shaft assembly 14, and out exhaust passage 144. Theairincavity274,duetothecavitycon?guration, transfer between these two components. Transmission 16 may therefore be designed in a manner that will reduce costs, such as choosing materials that may be used in a cooler environment than would exist ifthe airPDF Image | RADIAL FLOW GAS TURBINE ENGINE WITH ANNULAR COMBUSTOR LINER
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